The flutter characteristics of a wing with morphing flap are analyzed based on computational fluid dynamics (CFD) method. The unsteady aerodynamic reduced order model (ROM) is constructed to model the morphing flap with high accuracy, and the effect of flap camber on the wing flutter boundary is investigated. Active suppression of aeroelastic response by controlling the flap deflection is validated through numerical simulations. A Linear Quadratic Gaussian (LQG) compensator is designed to explore the potential of suppressing wing flutter by deflecting the flap actively. The simulation results show that the order of morphing flap camber may change the critical flutter speed and flutter frequency of the wing. Compared with the conventional plain flap, the morphing flap shows higher control efficiency with fewer deflection demands.

基于计算流体力学（CFD）方法，分析了具有变形襟翼的机翼的颤振特性。建立了非稳态气动降阶模型（ROM），以对变形襟翼进行高精度建模，并研究了襟翼弯度对机翼扑翼边界的影响。通过数值模拟验证了通过控制襟翼偏转对气动弹性响应的主动抑制。线性二次高斯（LQG）补偿器设计用于探索通过使襟翼主动偏转来抑制机翼颤动的潜力。仿真结果表明，襟翼弯度的变化顺序可能会改变机翼的临界颤振速度和颤振频率。与传统的普通襟翼相比，变形襟翼显示出更高的控制效率和更少的偏转需求。